EP3266711A1 - Runback ice formation control - Google Patents
Runback ice formation control Download PDFInfo
- Publication number
- EP3266711A1 EP3266711A1 EP17180370.3A EP17180370A EP3266711A1 EP 3266711 A1 EP3266711 A1 EP 3266711A1 EP 17180370 A EP17180370 A EP 17180370A EP 3266711 A1 EP3266711 A1 EP 3266711A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- gutter
- protection system
- recited
- ice protection
- aircraft surface
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Withdrawn
Links
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/16—De-icing or preventing icing on exterior surfaces of aircraft by mechanical means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1476—Canopies; Windscreens or similar transparent elements
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
- B64C39/12—Canard-type aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C5/00—Stabilising surfaces
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
Definitions
- the present disclosure relates to ice protection systems, and more particularly to such systems as used in aerospace applications.
- Runback ice forms aft of heated zones on thermal ice protection systems, e.g., on aircraft wings and empennage. This is due to water flowing aft after ice has shed and the surface has yet to cool. Runback ice can form in a ridge which can potentially affect lift, drag, and aircraft flying characteristics. Various methods can be used to control runback ice formation in an electrical or hot air heated system, but these may result in higher power consumption.
- An ice protection system includes an aircraft surface and a gutter defined in the aircraft surface between raised rails.
- the gutter includes a mouth that narrows into a trailing portion of the gutter.
- the mouth is configured to channel water runback rivulets into the trailing portion of the gutter.
- the gutter can be a first gutter of a plurality of side by side gutters, each including a respective mouth narrowing into a respective trailing portion, wherein the gutters are separated from one another by respective rails.
- the aircraft surface can be a surface of an airfoil, wherein the airfoil includes a leading edge and a trailing edge with the aircraft surface extending at least part way between the leading edge and the trailing edge.
- the gutter can extend in a direction from the leading edge to the trailing edge.
- the aircraft surface can include at least one of a parting strip or a shedding zone forward of the mouth of the gutter.
- the gutter can include at least one of an ice phobic or hydrophobic surface material for prevention of ice formation in the gutter.
- the gutter can include a heater configured to locally heat the gutter for prevention of ice formation in the gutter.
- each gutter in a plurality of gutters can include a respective heater configured to locally heat the gutter for prevention of ice formation in the gutter, and the heaters of the gutters can be spaced apart so areas of the aircraft surface between the gutters is free of heaters.
- the gutter can terminate at a tube leading under a wing surface for removing water to a drain either through natural or induced suction, wherein the tube is heated to prevent freezing.
- the trailing portion of the gutter can terminate at a protrusion that protrudes above an area of the aircraft surface adjacent to the protrusion for shedding a runback rivulet away from the aircraft surface.
- the gutter can have a depth of between 0.0005 inches (0.0127 mm) to 0.007 inches (0.1778 mm) relative to the rails.
- the aircraft surface can be configured to be mounted to an airframe over an underlying aerodynamic surface.
- the aircraft surface can be formed directly as an aerodynamic surface of an air frame.
- the aircraft surface can be configured as part of at least one of a wing, empennage, a cowl, a propeller or fan blade, a canard, a windshield, or the like.
- FIG. 1 a partial view of an exemplary embodiment of an aircraft surface in accordance with the disclosure is shown in Fig. 1 and is designated generally by reference character 100.
- FIGs. 2-8 Other embodiments of aircraft surfaces in accordance with the disclosure, or aspects thereof, are provided in Figs. 2-8 , as will be described.
- the systems and methods described herein can be used to control icing runback.
- Ice protection system 100 includes an aircraft surface 102 and a gutter 104 defined in the aircraft surface 102 between raised rails 106.
- the gutter 104 includes a mouth 108 that narrows into a trailing portion 110 of the gutter 104.
- the mouth 108 is configured to channel water runback rivulets into the trailing portion 110 of the gutter 104.
- the gutters 104 are separated from one another by respective rails 106.
- the exemplary aircraft surface 102 is a surface of an airfoil 112.
- the airfoil 112 includes a leading edge 114 and a trailing edge 116, wherein the aircraft surface 102 extends at least part way between the leading edge 114 and the trailing edge 116.
- the gutter 104 extends in a direction D from the leading edge 114 to the trailing edge 116.
- the aircraft surface 102 can includes a parting strip 118, configured for continuous heating above freezing for ice protection, and one, two, or more shedding zones 120 and 122 configured for cyclical heating to periodically remove accumulated ice.
- the parting strip 118 and shedding zones 120 and 122 are located forward of the mouths 108 of the gutter 104 so that runback water will form into rivulets in mouths 108, and the rivulets will be directed through trailing portions 110 of the gutters 104.
- the gutters 104 can extend all of the way to the trailing edge 116, and as indicated by the droplets in Fig. 2 , the rivulets can be shed from aircraft surface 102 at the trailing edge 116.
- Fig. 3 shows the cross-section of one of the mouths 108 between rails 106
- Fig. 4 shows the narrower trailing portion 110 aft of the mouth 108.
- the mouths 108 act as funnels to collect moisture from parting strip 118 and shedding zones 120 and 122, forming the rivulets which are guided along trailing portions 110 of the gutters 104.
- the gutter 104 can have a depth d of between 0.0005 inches (0.0127 mm) to 0.007 inches (0.1778 mm) relative to the rails 106, or any other suitable depth tailored for a given application.
- the depth d can be small enough to have little or no effect on aerodynamics.
- the gutter 104 can include a surface material 124 that is ice phobic and/or hydrophobic for prevention of ice formation in the gutter 104, and the rails can be of a non-hydrophobic/non-ice phobic material. It is also contemplated that the gutter 104 can include a heater 126 configured to locally heat the gutter 104 for prevention of ice formation in the gutter.
- each gutter 104 in the plurality of gutters 104 of Fig. 2 can include a respective heater 126 (not shown in Fig. 2 , but see Fig.
- heaters 126 of the gutters can be spaced apart so areas 128 of the aircraft surface 102 between the gutters 104 are free of heaters 126.
- the heaters 126 can be effective, even with relatively low power, as all they need to accomplish is to prevent the water in rivulets from freezing in gutters 104.
- the heaters 126 and or surface material 124 can extend into mouths 108 as indicated in Fig. 3
- each gutter 104 can terminate at a protrusion 130 that protrudes above an area of the aircraft surface 102 adjacent to the protrusion 130 for shedding a runback rivulet away from the aircraft surface 102.
- the protrusion 130 is curvilinear, however as shown in Fig. 7 another embodiment of protrusion 230 is v-shaped, and those skilled in the art will readily appreciate that any other suitable protrusion shape can be used without departing from the scope of this disclosure. As indicated schematically in Fig.
- the gutter 110 can optionally terminate at a tube 132 leading under a wing surface for removing water to a drain either through natural or induced suction, wherein the tube 132 is heated to prevent freezing.
- the tube 132 can be used in addition to or in lieu of protrusion 130.
- the aircraft surface 102 can be configured to be mounted to an airframe 10 over an underlying aerodynamic surface 12 as indicated by the large arrow on Fig. 8 . It is also contemplated that the aircraft surface 102 can be formed directly as an aerodynamic surface of an air frame, e.g. as in the aircraft surface 102 shown formed directly on wing 14 in Fig. 8 .
- the aircraft surface 102 can be configured as part of at least one of a wing 14, empennage 16, a cowl 18, or a fairing 20 such as for a drain, sensor, propeller or fan blade 22, canard 24, windshield 26, or the like.
Abstract
Description
- The present disclosure relates to ice protection systems, and more particularly to such systems as used in aerospace applications.
- Runback ice forms aft of heated zones on thermal ice protection systems, e.g., on aircraft wings and empennage. This is due to water flowing aft after ice has shed and the surface has yet to cool. Runback ice can form in a ridge which can potentially affect lift, drag, and aircraft flying characteristics. Various methods can be used to control runback ice formation in an electrical or hot air heated system, but these may result in higher power consumption.
- Such conventional methods and systems have generally been considered satisfactory for their intended purpose. However, there is still a need in the art for improved runback control. The present disclosure provides a solution for this need.
- An ice protection system includes an aircraft surface and a gutter defined in the aircraft surface between raised rails. The gutter includes a mouth that narrows into a trailing portion of the gutter. The mouth is configured to channel water runback rivulets into the trailing portion of the gutter.
- The gutter can be a first gutter of a plurality of side by side gutters, each including a respective mouth narrowing into a respective trailing portion, wherein the gutters are separated from one another by respective rails.
- The aircraft surface can be a surface of an airfoil, wherein the airfoil includes a leading edge and a trailing edge with the aircraft surface extending at least part way between the leading edge and the trailing edge.
- The gutter can extend in a direction from the leading edge to the trailing edge.
- The aircraft surface can include at least one of a parting strip or a shedding zone forward of the mouth of the gutter.
- The gutter can include at least one of an ice phobic or hydrophobic surface material for prevention of ice formation in the gutter.
- It is also contemplated that the gutter can include a heater configured to locally heat the gutter for prevention of ice formation in the gutter. For example each gutter in a plurality of gutters can include a respective heater configured to locally heat the gutter for prevention of ice formation in the gutter, and the heaters of the gutters can be spaced apart so areas of the aircraft surface between the gutters is free of heaters.
- The gutter can terminate at a tube leading under a wing surface for removing water to a drain either through natural or induced suction, wherein the tube is heated to prevent freezing.
- The trailing portion of the gutter can terminate at a protrusion that protrudes above an area of the aircraft surface adjacent to the protrusion for shedding a runback rivulet away from the aircraft surface.
- The gutter can have a depth of between 0.0005 inches (0.0127 mm) to 0.007 inches (0.1778 mm) relative to the rails.
- The aircraft surface can be configured to be mounted to an airframe over an underlying aerodynamic surface.
- It is also contemplated that the aircraft surface can be formed directly as an aerodynamic surface of an air frame.
- The aircraft surface can be configured as part of at least one of a wing, empennage, a cowl, a propeller or fan blade, a canard, a windshield, or the like.
- These and other features of the systems and methods of the subject disclosure will become more readily apparent to those skilled in the art from the following detailed description of the preferred embodiments taken in conjunction with the drawings.
- So that those skilled in the art to which the subject disclosure appertains will readily understand how to make and use the devices and methods of the subject disclosure without undue experimentation, preferred embodiments thereof will be described in detail herein below with reference to certain figures, wherein:
-
Fig. 1 is a schematic perspective view of an exemplary embodiment of an aircraft surface constructed in accordance with the present disclosure, showing the gutters for runback control; -
Fig. 2 is a schematic plan view of the aircraft surface ofFig. 1 , showing the mouth and trailing portions of the gutters; -
Fig. 3 is a schematic cross-sectional view of the aircraft surface ofFig. 1 , showing the cross-section of the mouth of one of the gutters; -
Fig. 4 is a schematic cross-sectional view of the aircraft surface ofFig. 1 , showing the cross-section of the trailing portion of one of the gutters; -
Fig. 5 is a schematic plan view of a portion of an exemplary embodiment of an aircraft surface, showing a trailing portion of a gutter terminating in a protrusion for shedding runback rivulets from the aircraft surface; -
Fig. 6 is a schematic cross-sectional elevation view of the aircraft surface ofFig. 5 , showing the protrusion extending above the surrounding surface; -
Fig. 7 is a schematic plan view of a portion of another exemplary embodiment of a protrusion for shedding runback rivulets, wherein the protrusion is triangular; and -
Fig. 8 is a schematic perspective view of an aircraft, showing various exemplary locations for aircraft surfaces constructed in accordance with the present disclosure. - Reference will now be made to the drawings wherein like reference numerals identify similar structural features or aspects of the subject disclosure. For purposes of explanation and illustration, and not limitation, a partial view of an exemplary embodiment of an aircraft surface in accordance with the disclosure is shown in
Fig. 1 and is designated generally byreference character 100. Other embodiments of aircraft surfaces in accordance with the disclosure, or aspects thereof, are provided inFigs. 2-8 , as will be described. The systems and methods described herein can be used to control icing runback. -
Ice protection system 100 includes anaircraft surface 102 and agutter 104 defined in theaircraft surface 102 between raisedrails 106. Thegutter 104 includes amouth 108 that narrows into atrailing portion 110 of thegutter 104. Themouth 108 is configured to channel water runback rivulets into thetrailing portion 110 of thegutter 104. There are a plurality of side byside gutters 104, each including arespective mouth 108 narrowing into a respectivetrailing portion 110, however for sake ofclarity mouth 108 andtrailing portion 110 are only identified on one of thechannels 104. Thegutters 104 are separated from one another byrespective rails 106. Theexemplary aircraft surface 102 is a surface of anairfoil 112. Theairfoil 112 includes a leadingedge 114 and atrailing edge 116, wherein theaircraft surface 102 extends at least part way between the leadingedge 114 and thetrailing edge 116. Thegutter 104 extends in a direction D from the leadingedge 114 to thetrailing edge 116. Theaircraft surface 102 can includes aparting strip 118, configured for continuous heating above freezing for ice protection, and one, two, ormore shedding zones - As shown in
Fig. 2 , theparting strip 118 and sheddingzones mouths 108 of thegutter 104 so that runback water will form into rivulets inmouths 108, and the rivulets will be directed throughtrailing portions 110 of thegutters 104. Thegutters 104 can extend all of the way to thetrailing edge 116, and as indicated by the droplets inFig. 2 , the rivulets can be shed fromaircraft surface 102 at thetrailing edge 116.Fig. 3 shows the cross-section of one of themouths 108 betweenrails 106, andFig. 4 shows the narrowertrailing portion 110 aft of themouth 108. Themouths 108 act as funnels to collect moisture fromparting strip 118 and sheddingzones portions 110 of thegutters 104. Thegutter 104 can have a depth d of between 0.0005 inches (0.0127 mm) to 0.007 inches (0.1778 mm) relative to therails 106, or any other suitable depth tailored for a given application. The depth d can be small enough to have little or no effect on aerodynamics. - With continued reference to
Fig. 4 , thegutter 104 can include asurface material 124 that is ice phobic and/or hydrophobic for prevention of ice formation in thegutter 104, and the rails can be of a non-hydrophobic/non-ice phobic material. It is also contemplated that thegutter 104 can include aheater 126 configured to locally heat thegutter 104 for prevention of ice formation in the gutter. For example eachgutter 104 in the plurality ofgutters 104 ofFig. 2 can include a respective heater 126 (not shown inFig. 2 , but seeFig. 4 ) configured to locally heat thegutter 104 for prevention of ice formation in thegutter 104, and theheaters 126 of the gutters can be spaced apart soareas 128 of theaircraft surface 102 between thegutters 104 are free ofheaters 126. Thus only a small area ofaircraft surface 102 needs to be heated and/or hydrophobic/ice phobic compared to traditional ice protection systems employing heaters or hydrophobic/ice phobic surface materials. It is possible forheaters 126 to be effective, even with relatively low power, as all they need to accomplish is to prevent the water in rivulets from freezing ingutters 104. Theheaters 126 and orsurface material 124 can extend intomouths 108 as indicated inFig. 3 - With reference now to
Figs. 5-6 , the trailingportion 110 of eachgutter 104 can terminate at aprotrusion 130 that protrudes above an area of theaircraft surface 102 adjacent to theprotrusion 130 for shedding a runback rivulet away from theaircraft surface 102. As shown inFig. 5 , theprotrusion 130 is curvilinear, however as shown inFig. 7 another embodiment ofprotrusion 230 is v-shaped, and those skilled in the art will readily appreciate that any other suitable protrusion shape can be used without departing from the scope of this disclosure. As indicated schematically inFig. 6 , thegutter 110 can optionally terminate at atube 132 leading under a wing surface for removing water to a drain either through natural or induced suction, wherein thetube 132 is heated to prevent freezing. Thetube 132 can be used in addition to or in lieu ofprotrusion 130. - Referring now to
Fig. 8 , theaircraft surface 102 can be configured to be mounted to anairframe 10 over an underlyingaerodynamic surface 12 as indicated by the large arrow onFig. 8 . It is also contemplated that theaircraft surface 102 can be formed directly as an aerodynamic surface of an air frame, e.g. as in theaircraft surface 102 shown formed directly onwing 14 inFig. 8 . Theaircraft surface 102 can be configured as part of at least one of awing 14,empennage 16, a cowl 18, or a fairing 20 such as for a drain, sensor, propeller orfan blade 22,canard 24,windshield 26, or the like. - The methods and systems of the present disclosure, as described above and shown in the drawings, provide for icing runback control with superior properties including reduced power requirements. While the apparatus and methods of the subject disclosure have been shown and described with reference to preferred embodiments, those skilled in the art will readily appreciate that changes and/or modifications may be made thereto without departing from the scope of the subject disclosure.
Claims (15)
- An ice protection system (100) comprising:an aircraft surface (102); anda gutter (104) defined in the aircraft surface (102) between raised rails (106), wherein the gutter (104) includes a mouth (108) that narrows into a trailing portion (110) of the gutter (104), wherein the mouth (108) is configured to channel water runback rivulets into the trailing portion (110) of the gutter (104).
- An ice protection system as recited in claim 1, wherein the gutter (104) is a first gutter (104) of a plurality of side by side gutters (104), each including a respective mouth (108) narrowing into a respective trailing portion (110), wherein the gutters (104) are separated from one another by respective rails (106).
- An ice protection system as recited in claim 1 or 2, wherein the aircraft surface (102) is a surface of an airfoil (112), wherein the airfoil (112) includes a leading edge (114) and a trailing edge (116) with the aircraft surface (102) extending at least part way between the leading edge (114) and the trailing edge (116).
- An ice protection system as recited in claim 3, wherein the gutter (104) extends in a direction (D) from the leading edge (114) to the trailing edge (116).
- An ice protection system as recited in any preceding claim, wherein the aircraft surface (102) includes at least one of a parting strip (118) or a shedding zone (120, 122) forward of the mouth (108) of the gutter (104).
- An ice protection system as recited in any preceding claim, wherein the gutter (104) includes at least one of an ice phobic or hydrophobic surface material (124) for prevention of ice formation in the gutter (104).
- An ice protection system as recited in any preceding claim, wherein the gutter includes a heater (126) configured to locally heat the gutter (104) for prevention of ice formation in the gutter (104).
- An ice protection system as recited in any preceding claim, wherein the gutter (104) terminates at a tube (132) leading under a wing surface for removing water to a drain either through natural or induced suction, wherein the tube (132) is heated to prevent freezing.
- An ice protection system as recited in any preceding claim, wherein the trailing portion (100) of the gutter (104) terminates at a protrusion (130; 230) that protrudes above an area of the aircraft surface (102) adjacent to the protrusion (130; 230) for shedding a runback rivulet away from the aircraft surface (102).
- An ice protection system as recited in any preceding claim, wherein the gutter (104) has a depth (d) of between 0.0005 inches (0.0127 mm) to 0.007 inches (0.1778 mm) relative to the rails (106).
- An ice protection system as recited in any preceding claim, wherein the gutter (104) is a first gutter (104) of a plurality of side by side gutters (104), each including a respective mouth (108) narrowing into a respective trailing portion (110), wherein the gutters (104) are separated from one another by respective rails (106), and wherein each gutter (104) includes a respective heater (126) configured to locally heat the gutter (104) for prevention of ice formation in the gutter (104).
- An ice protection system as recited in claim 11, wherein the heaters (126) of the gutters (104) are spaced apart so areas (128) of the aircraft surface (102) between the gutters (104) is free of heaters (126).
- An ice protection system as recited in any preceding claim, wherein the aircraft surface (102) is configured to be mounted to an airframe (10) over an underlying aerodynamic surface (12).
- An ice protection system as recited in any of claims 1 to 12, wherein the aircraft surface (102) is formed directly as an aerodynamic surface of an air frame (10).
- An ice protection system as recited in any preceding claim, wherein the aircraft surface (102) is configured as part of at least one of a wing (14), empennage (16), a cowl (18), a propeller or fan blade (22), a canard (24), or a windshield (26).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/205,446 US10252807B2 (en) | 2016-07-08 | 2016-07-08 | Runback control |
Publications (1)
Publication Number | Publication Date |
---|---|
EP3266711A1 true EP3266711A1 (en) | 2018-01-10 |
Family
ID=59298407
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP17180370.3A Withdrawn EP3266711A1 (en) | 2016-07-08 | 2017-07-07 | Runback ice formation control |
Country Status (4)
Country | Link |
---|---|
US (1) | US10252807B2 (en) |
EP (1) | EP3266711A1 (en) |
BR (1) | BR102017014550A2 (en) |
CA (1) | CA2972874A1 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3738884A1 (en) * | 2019-05-16 | 2020-11-18 | Goodrich Corporation | Pneumatic deicer with runback channels |
CN112977836A (en) * | 2021-05-11 | 2021-06-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing device |
Families Citing this family (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE1024827B1 (en) * | 2016-12-15 | 2018-07-17 | Safran Aero Boosters S.A. | AUB GLACIOPHOBE OF AXIAL TURBOMACHINE COMPRESSOR |
US10875632B2 (en) * | 2017-11-08 | 2020-12-29 | Goodrich Corporation | Ice phobic material to reduce runback ice |
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WO1984003867A1 (en) * | 1983-04-05 | 1984-10-11 | Anders Edvard Hugo Malmstroem | Method and means for preventing wall turbulence |
US5322246A (en) * | 1991-08-12 | 1994-06-21 | Mcdonnell Douglas Corporation | Ice prevention device for airfoils |
US20080029648A1 (en) * | 2004-03-03 | 2008-02-07 | Giamati Michael J | Aircraft wing with electrothermal deicing and/or anti-icing device |
US20110198444A1 (en) * | 2010-02-16 | 2011-08-18 | The Boeing Company | Aerodynamic structure having a ridged solar panel and an associated method |
EP2862804A1 (en) * | 2013-10-17 | 2015-04-22 | Airbus Helicopters | Anti-icing device for aircraft blades |
FR3025741A1 (en) * | 2014-09-15 | 2016-03-18 | Airbus Group Sas | MULTIFUNCTIONAL ADHESIVE FILM FOR SURFACE PROTECTION OF WORKPIECES |
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US3463418A (en) | 1968-03-20 | 1969-08-26 | Edmond S Miksch | Vortex generator for airplane wing |
US5921502A (en) * | 1996-06-19 | 1999-07-13 | Cox & Company, Inc. | Hybrid ice-protection system for use on roughness-sensitive airfoils |
US6279856B1 (en) * | 1997-09-22 | 2001-08-28 | Northcoast Technologies | Aircraft de-icing system |
US20070031639A1 (en) * | 2005-08-03 | 2007-02-08 | General Electric Company | Articles having low wettability and methods for making |
EP2307740B1 (en) * | 2008-08-05 | 2016-05-04 | Alcoa Inc. | Metal sheets and plates having friction-reducing textured surfaces and methods of manufacturing same |
GB0922285D0 (en) * | 2009-12-22 | 2010-02-03 | Rolls Royce Plc | Hydrophobic surface |
US9827735B2 (en) * | 2012-03-09 | 2017-11-28 | United Technologies Corporation | Erosion resistant and hydrophobic article |
US20160114883A1 (en) * | 2014-10-23 | 2016-04-28 | The Boeing Company | Actively-controlled superhydrophobic surfaces |
-
2016
- 2016-07-08 US US15/205,446 patent/US10252807B2/en not_active Expired - Fee Related
-
2017
- 2017-07-05 BR BR102017014550-6A patent/BR102017014550A2/en not_active Application Discontinuation
- 2017-07-07 EP EP17180370.3A patent/EP3266711A1/en not_active Withdrawn
- 2017-07-07 CA CA2972874A patent/CA2972874A1/en not_active Abandoned
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
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WO1984003867A1 (en) * | 1983-04-05 | 1984-10-11 | Anders Edvard Hugo Malmstroem | Method and means for preventing wall turbulence |
US5322246A (en) * | 1991-08-12 | 1994-06-21 | Mcdonnell Douglas Corporation | Ice prevention device for airfoils |
US20080029648A1 (en) * | 2004-03-03 | 2008-02-07 | Giamati Michael J | Aircraft wing with electrothermal deicing and/or anti-icing device |
US20110198444A1 (en) * | 2010-02-16 | 2011-08-18 | The Boeing Company | Aerodynamic structure having a ridged solar panel and an associated method |
EP2862804A1 (en) * | 2013-10-17 | 2015-04-22 | Airbus Helicopters | Anti-icing device for aircraft blades |
FR3025741A1 (en) * | 2014-09-15 | 2016-03-18 | Airbus Group Sas | MULTIFUNCTIONAL ADHESIVE FILM FOR SURFACE PROTECTION OF WORKPIECES |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3738884A1 (en) * | 2019-05-16 | 2020-11-18 | Goodrich Corporation | Pneumatic deicer with runback channels |
US11117672B2 (en) | 2019-05-16 | 2021-09-14 | Goodrich Corporation | Pneumatic deicer with runback channels |
CN112977836A (en) * | 2021-05-11 | 2021-06-18 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing device |
CN112977836B (en) * | 2021-05-11 | 2021-08-10 | 中国空气动力研究与发展中心低速空气动力研究所 | Anti-icing device |
Also Published As
Publication number | Publication date |
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US10252807B2 (en) | 2019-04-09 |
CA2972874A1 (en) | 2018-01-08 |
US20180009538A1 (en) | 2018-01-11 |
BR102017014550A2 (en) | 2018-01-23 |
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